GB978846A - Improvements in and relating to aircraft - Google Patents

Improvements in and relating to aircraft

Info

Publication number
GB978846A
GB978846A GB35789/63A GB3578963A GB978846A GB 978846 A GB978846 A GB 978846A GB 35789/63 A GB35789/63 A GB 35789/63A GB 3578963 A GB3578963 A GB 3578963A GB 978846 A GB978846 A GB 978846A
Authority
GB
United Kingdom
Prior art keywords
lever
control
levers
movement
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB35789/63A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dornier Werke GmbH
Original Assignee
Dornier Werke GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Dornier Werke GmbH filed Critical Dornier Werke GmbH
Publication of GB978846A publication Critical patent/GB978846A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0091—Accessories not provided for elsewhere
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/20—Control lever and linkage systems
    • Y10T74/20012—Multiple controlled elements
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/20—Control lever and linkage systems
    • Y10T74/20207—Multiple controlling elements for single controlled element

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Mechanical Control Devices (AREA)

Abstract

978,846. Controlling aircraft. DORNIER-WERKE G.m.b.H. Sept. 11, 1963 [Sept. 14, 1962], No. 35789/63. Heading B7G. An aircraft control transmission includes two lever arms 8, 9 (Figs. 1 and 2), of equal length, pivotally connected together at one end b, the angle between the arms being varied according to the aircraft's forward speed to vary the transmission ratio of the linkage. The aircraft described is fitted with direct lift engines, whose fuel flow control 3 is coupled to the aileron control, for lateral control, through the levers 8, 9 and a further lever 6 which is movable longitudinally by a further lever 5, about which the lever 6 pivots, actuated by a dynamic pressure sensor 4. Fig. 1 shows the high speed configuration in which movement of the control stick 1 does not affect the fuel control 3, but only the aileron 2, and Fig. 2 shows the low speed configuration in which movement of the control stick causes levers 8 and 9 to rotate about a pivot c, and lever 6 to rotate about the lever 5 to actuate the fuel control 3. In a modification (Fig. 4), equal length levers 23, 24 are provided, the lever 23 being rotatable about the pivot g connecting them by a rod 28 leading to a dynamic pressure sensor. When the levers 23, 24 are thus relatively angularly displaced, movement of a rod 27 connected to the control stick causes the levers 23, 24 to rotate about the shaft and actuates the fuel control by rotating a rod 26. In a further modification (Fig. 7) the lever 23 is replaced by a disc 23<SP>1</SP> rotatably mounted in a disc 21<SP>1</SP> rotatable by the dynamic pressure sensor through a rod 28<SP>1</SP>. When the disc 211 is thus rotated so that the pivot h<SP>1</SP> of the levers 24<SP>1</SP>, 26<SP>1</SP> is not aligned with the centre of the disc 23<SP>1</SP>, movement of the lever 25<SP>1</SP> connected to the control stick will produce movement of the lever 26<SP>1</SP> leading to the fuel control. The apparatus may also be used for pitch and yaw control and may be adapted to vary the lift engine nozzle area instead of its fuel flow. The speed may alternatively be sensed by radar equipment.
GB35789/63A 1962-09-14 1963-09-11 Improvements in and relating to aircraft Expired GB978846A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DED39844A DE1225502B (en) 1962-09-14 1962-09-14 Control device for aircraft with slow flight or hover characteristics, in particular aircraft taking off and landing vertically

Publications (1)

Publication Number Publication Date
GB978846A true GB978846A (en) 1964-12-23

Family

ID=7044999

Family Applications (1)

Application Number Title Priority Date Filing Date
GB35789/63A Expired GB978846A (en) 1962-09-14 1963-09-11 Improvements in and relating to aircraft

Country Status (3)

Country Link
US (1) US3168265A (en)
DE (1) DE1225502B (en)
GB (1) GB978846A (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3282125A (en) * 1963-12-23 1966-11-01 Gen Motors Corp Vehicle control pedals
US3309937A (en) * 1965-02-02 1967-03-21 Piasecki Aircraft Corp Coordinating control linkage
US3957226A (en) * 1975-01-27 1976-05-18 The Boeing Company Helicopter yaw and propulsion mechanism
US4088039A (en) * 1977-02-14 1978-05-09 The Boeing Company Ratio changing mechanism
US4362067A (en) * 1980-08-21 1982-12-07 The Garrett Corporation Variable authority trim mixer
US4401077A (en) * 1981-04-17 1983-08-30 The Garrett Corporation Throttle linkage control
FR2946317B1 (en) * 2009-06-04 2011-06-17 Eurocopter France GUIGNOL A VARIABLE RATIO FOR MANUAL AIRCRAFT FLIGHT CONTROL CHAIN WITH ROTATING CAR

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2191250A (en) * 1934-09-24 1940-02-20 Siemens App Und Maschinen Gmbh System for the automatic control of airplanes
US2205610A (en) * 1937-06-07 1940-06-25 Arado Flugzeugwerke Gmbh Safety control for aircraft
DE723154C (en) * 1937-06-08 1942-07-30 Arado Flugzeugwerke G M B H Safety control device for aircraft
US2596242A (en) * 1949-05-12 1952-05-13 Glenn L Martin Co Variable ratio booster control system
US3065939A (en) * 1957-07-12 1962-11-27 Rech Etudes Prod Control system for aircraft
US3114520A (en) * 1961-01-16 1963-12-17 Ryan Aeronautical Co Stabilization and control system for pilotless, vertical take-off and landing aircraft
US3069117A (en) * 1961-03-02 1962-12-18 Short Brothers & Harland Ltd Aircraft adapted for vertical take-off and landing

Also Published As

Publication number Publication date
US3168265A (en) 1965-02-02
DE1225502B (en) 1966-09-22

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